Airplane



Dec. 12, 1944.

V. N. DlVOZZl AIRPLANE Filed Sept. 1l, 1941 4 Sheets-Sheet l INVENTOR.

ATTURNEYS.

Dec. 12, 1944.

v. N. Dl vozzl 2,364,956

AIRPLANE Filed Sept. 1l, 1941 4 Sheets-Sheet 2 ATTORNEYS Dec. l2, 1944. v. N. Dl'vozzl AIRPLANE Filed sept. 11, '1941 4 Sheets-Sheet 5 Guzzi' Dec. l2, 1944.

V. N. DI'VOZZI AIRPLANE Filed Sept. ll, 1941 4 Sheets-Sheet 4 means for translating movement into the desired arcuate movement at the ends for further effecting control of the airplane.

With reference to the drawings, the main fixed framework of the airplane is designed generally 23, I having shown only such portions of it as are connected to other parts which enter into the inventive structure herein disclosed. Supported upon this framework 23 are upright posts 2| which carry a lower annulus 22 having bosses 23 secured to these posts 2|, while there is an upper annulus 24 similarly supported. Additional posts 25 secured to both annuluses extend upwardly therefrom for supporting the bed 25 on which the cradle 21 is pivoted as at 28 for rockably mounting the engine or motor 23 pivotally with relation t the bed.

A wing carrier. designated generally 33, is of a squirrel-cage type construction (see Figs. 2 and 12) and consists of a lower annular plate 3| and an upper annular plate 32 with vertical rods 33 extending between these plates and connecting them together in vertically spaced rigid parallel relationship. An annular gear 34 is cut upon the top of the plate 32. This squirrel-cage carrier 33 has a portion of its plate 32-located above and in spaced relation to the plate 24 (see Fig. 9) with anti-friction rollers 35 between the two plates, while the plate 3| extends beneath-and under the plate 22 which is provided with antifriction rollers 35. 'Ihese rollers are mounted on the xed plates 24 and 22 by means of spaced concentric anges 33 and 31 (see Fig. 8) with the rollers 35 provided with trunnions 38 extending into suitable notches in the flanges so as to retain them in place. 'Ihese flanges 33 and 31 may be secured in any suitable manner, such, for instance, as by welding, to the plates 22 and 24 to retain them in desired relation.

A pinion 43 is supported as at 42 (see Figs. 1, 2, 3, 4) by braces from the plate 24 and is in constant mesh with the ring gear 34. The shaft 43 is secured to the pinion 43 and drives the same through universal joint 44 which is provided with a clutch coupling 45 operable by forked arm 43 and handle 41 (see Fig. 4). This clutch coupling is slidable on the shaft 43 and is provided with a slot 48 to connect with the reduced key 43 by a head 53 on a shaft 5| which is driven by bevel gear 52 in mesh with bevel gear 53 which is driven by the motor 23.

When it is desired that the motor shall drive the wing carrier, the handle 54, which attaches to the bearing 55 for the shaft 5| and which is also fixed to the cradle 21 upon which the motor is mounted, is swung so that the motor swings about the pivot 28 fixed on the support bars 23 secured to the posts 25. This action positions the shaft substantially in alignment with the shaft 43 which drives the pinion 43. The handle 41 is then manipulated toslide the clutch coupling so that the slot 48 receives the key portion 43; -and then the engine will operate the bevel gear 43 and the ring 34 for rotation of the cage-like structure which carries the wings.

The wing carrier 33 is mounted in a generally cubical frame (see Figs. 11 and l2.) consisting of vertical bars 63, bars 6| extending longitudinally of the airplane, and bars 32 extending crosswise of the airplane. The bars 62 are constructed to form the leading and trailing edges of a wing fixed to the cage which has a center bar 33 and other bracing bars such as 34 extending upwardly to meet the bar 33. This wing is fixed to the carrier 33 so as to rotate therewith and is maintained in a permanent position with reference to the carrier. Connections between the rods of the frame are of any suitable construction, I having shown coupling joints at the crossings for reinforcement and for secure connection, although other arrangements may be provided.

The other wing is attached to the carrier in such a manner that it may be tilted about its center; and this wing frame is therefore a complete unit in itself mounted on the carrier for movement and comprises a bar 35 for the leading edge and bar 33 for the trailing edge with a center bar 31 running lengthwise of the wing and about which point as an axis the wing may pivot. Reinforcement by brace bars 33 is provided between the bars 35 and 31 and bars 33 and 31.l At the inner edge of the wing, brace bars 33 extend from a point 13 beneath the bars 33 to vertical 14 to the carrier frame and may rock about the axis of the bar 31 as a center by sufficient looseness being provided in these slots. 'Ihe links 13 are connected together by a link 15 pivoted as at 13 so that motion will be transmitted oppositely to the links 13 and whereby the leading edge 35, which is normally elevated, may be lowered, while the trailing edge will be raised to provide an opposite elevation from that which is usually provided.

I lock the wing in a position so that the leading edge 35 will be elevated and the wings on either side will be in alignment as illustrated in Fig. i3. This lock (see Fig. 5) consists of a pin 11 urged by spring 13 into a-position so as to enter an opening 13 (see Fig. l0) in a bell crank arm 33 on shaft 3| supported as at 32 and connected by crank 33 and link 34 to the linkage 13 (see Fig. 13). When this pin is retracted by handle 35 (see Fig. 5) and held in position by a dog 33 in one of the notches 31, the wing is free to be tilted about the axis 31 as a center; and this tilting is performed by a spring 33 (see Fig. 14) supported on the end of the rod 1| which is retained in position by bracket 32. The spring engages beneath the trailing edge 33 of the wing frame on the guide pin 3|; and when the lock pin is released, this spring urges this trailing edge upwardly, and the leading edge will pivot downwardly about the axis 31 to give the desired inclination to the wing (see Fig. 1'1). This wing tilting will be performed just prior to, or simultaneously with the swinging of the motor into position so as t0 drive the ring gear and cause the wings to rotate about a vertical axis n the heliocopter principle.

In Fig. 16, I have illustrated va rudder |33 and elevators |3|. These are controlled by rods one above the other, as |32 and |33, mounted in bearings, as |34 and |35, and which rotate about their longitudinal central axis. The rudder control is operable by the lower rod |33 which at its inboard end (see Fig. l) is connected to gears |33 and |31, the latter gear being swingable by shaft |33 and handle |33.' The shaft |33 has its bearing at ||3. At the outboard end (see Fig. 16) of rod |33, there is a gear mounted to mesh with bevel gear I2 which is secured to the shaft I3 for swinging the rudder |33.

The elevators are controlled by shaft |32 which at its inboard end (see Fig. l) has meshing segmental gears l |4 and I I5, the latter being mounted on rod ||3 swingable by handle ||1 and having a bearing at III. At the outboard end of this rod (see Fig. 19), there is a bevel gear Il! meshing with another bevel gear |20 secured to shaft I2I and which upon rotation will swing the elevators IBI about this shaft as an axis to provide the inclination for the control of the airplane.

If it is desired to descend, the wings, designated i2! and |26, will be rotated as illustrated in the dot-dash lines: and at the same time the propeller i2'i will be tipped upwardly as illustrated in Fig. 4 so that some upward sustaining force will be provided.

By this arrangement, it will of course be apparent that much less area need be provided for landing the airplane than were the wings flxd and their support dependent by their forward mo tion through the air.

I claim:

l. In an airplane having main supporting wings rotatable about a vertical axis, a traction propeller for driving said airplane the blades of which normally extend into the path of rotation of said wings, and means for moving said blades out of said path of rotation when said wings are rotated.

2. In an airplane having main supporting wings rotatable about a vertical axis, a traction propeller for driving said airplane and mounted above said wings and having the blades thereof normally extending into the path of rotation of said Wings. and means for movin'g said blades out of said path of rotation when said wings are rotated.

3. In an airplane having main supporting wings rotatable about a vertical axis, a motor movably mounted at a position located above said wings, a propeller attached to said motor and driven thereby and movable therewith, the blades of said propeller normally extending into the path oi' rotation of said wings, and means for moving said motor to move said blades out oi said path of rotation when said wings are rotated.

VINCENT N. DI VOZZI. 

